Robotic Pre-Cursor Contribution to Human NEA Mission
H. Kuninaka JSPEC/JAXA Asteroid Explorer “Hayabusa”
Dimensions ����1.0m x 1.6m x 1.1m Weight : 380kg(Dry) Chemical Fuel 70kg Xe Propellant 60kg Total 510kg Electric Power : 2.6kW@Earth Communication : X band Arrival at Asteroid on September 12, 2005 Results of Hayabusa Before After
4 Resolution Radar �100m
Pre HAYABUSA
Post HAYABUSA Telescope Sample Return �AU �1µm (10-6m) (1012m)
Rendezvous �1m
Landing��1mm Improvement Atomic Analysis on 22 orders of magnitude �1� (10-10m) Contribution to NEOs exploration Lessons Learned from Hayabusa Optical Navigation in Approach from Heliocentric Space
OD ambiguity of 1! on July 29, 2005 Position Velocity R&RR 1,800km 72cm/s Optical 45km 6cm/s
Image of Itokawa taken by STT Contribution to NEOs exploration Lessons Learned from Hayabusa Landmark Navigation in Proximity Operation
Relative Position Determination against Asteroid Terrain Contour Matching Guidance comparing Actual Image with CG
Far Field <= Outline of Asteroid Near Field <= Geographical Features Contribution to NEOs exploration Lessons Learned from Hayabusa
Autolanding in Zero Gravity Field
Descent Sequence Actual Images in Descent Contribution to NEOs exploration Lessons Learned from Hayabusa
Redundancy against malfunctions in long flight Spirit to accomplish space mission
Beacon Communication Bypath circuit of Ion Engines What is Hayabusa2 ? (Summary) • Hayabusa2 is the follow-on mission of Hayabusa. • It is the sample return mission from a C-type asteroid. (The target asteroid is 1999 JU3.) • The mission objectives are science and engineering. Science : origin and evolution of the solar system, the origin of organic matters and water Engineering : more robust and reliable system for sample return mission, challenge for new technology • On May 1, 2011, the status of project becomes officially Phase-B. Hayabusa2 project team has budget to develop the spacecraft from the fiscal year of 2011. PDR has almost finished now and CDR will be done at the end of 2011. • Schedule: the launch: 2014 (2015 backup), asteroid arrival: 2018, asteroid departure: 2019, the earth return: 2020 • International collaborations with Germany, USA, Australia, and
other countries are currently (or will be) under discussions. 10 Primitive Body Exploration Program Considered in Japan
Hayabusa Post Hayabusa Hayabusa-2 Hayabusa-Mk-II 2003 - 2010 2014-
Itokawa 1999 JU3 Wilson-Harrington? D-type Asteroid?
C-type S-type D-type
Main Asteroid Belt 11 Target Asteroid : 1999 JU3
Orbit Itokawa Rotation period: 0.3178day (~7.6 h) )(331, 20), (73, -62) Kawakami Model Mueller Model Axis ratio = 1.3 : 1.1 : 1.0 Mars Size : 0.922 ± 0.048 km Earth Albedo : 0.063 ± 0.006 H=18.82 ± 0.021, G=0.110 ± 0.007 Type : Cg
Shape model by Kawakami 12 Mission Outline of Hayabusa-2
Launch June 2018 : Arrival at 1999 JU3 Global observation of the asteroid, July 2014 deployment of small rover/lander, Mothership carries multiple samplings an impactor. Sample analysis New Experiment
Earth Return Dec. 2020
Dec. 2019 : Departure
2019 The impactor collides to the surface of the asteroid. Further exploration 13 Hayabusa-2 Mission Schedule year 2014 2015 2016 2017 2018 2019 2020 month 07 12 06 12 06 08 12 12
Spacecraft IES operation
(Back-up windows) Launch Earth Swing-by Departure Earth Arrival at Science from 1999 return 1999JU3 observation JU3 , Sampling IES operation Impactor
14 Hayabusa2 Spacecraft under consideration
High gain antenna (Ka) High gain Solar array antenna (X) paddle Small lander MASCOT
Reentry capsule
Small rover Sampler Impactor Ion engine
15 Nominal Payloads for Science Payloads Specifications
Multiband Imager Wavelength: 0.4 – 1.0 mm, FOV: 5.7 deg x 5.7 deg, Pixel Number: 1024 (AMICA) x 1024 px filter (ul, b, v, w, x, p) (Heritage of Hayabusa) Near IR Spectrometer Wavelength: 1.8 – 3.2 mm, FOV: 0.1 deg x 0.1 deg (NIRS3) (Heritage of Hayabusa, but 3mm range is new) Thermal IR Imager Wavelength: 8 – 12 mm, FOV: 12 deg x 16 deg, Pixel Number: 320 x 240 (TIR) px (Heritage of Akatsuki) Laser Altimeter Measurement Range: 50 m – 50 km(Heritage of Hayabusa) (LIDAR) Sampler Minor modifications from Hayabusa-1 (Heritage of Hayabusa) Small Carry-on Impactor Small, deployed system to form an artificial crater on the surface (New)
Small Rover Almost same as MINERVA of Hayabusa-1 (MINERVA-2) (possible payload: Cameras, thermometers) (Heritage of Hayabusa) Small Rover Supplied from DLR (MASCOT) microOmega, MAG, CAM, MARA
16 Possible International Collaborations Germany - DLR: JAXA: Carry a DLR's small lander MASCOT on board. DLR : Tracking support (Ka, X band), Support of small gravity experiment both : science collaboration USA – NASA, OSIRIS REx: JAXA-NASA: Similar collaboration like Hayabusa1 (Tracking support, Sample, Science, etc.) Australia: Similar collaboration like Hayabusa1 (Capsule recovery, Science, etc.) Other countries: 17 Summary
Hayabusa and Hayabusa2 will contribute to Human NEA Mission Optical Navigation in approch to asteroid from heliocentric space Landmark Navigation in proximity operation around asteroid Autolanding in zero gravity field Redundancy against malfunctions in long flight Spirit to accomplish space mission Information and Knowledge on C-type asteroid
Robotic Pre-Cursor will contribute to Human NEA Mission Technology Demonstration in advance On-the-spot Investigation on target asteroid
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